Tri-propellant rocket engine for space launch applications

Abstract

A tri-propellant rocket engine for space launch applications is disclosed. The tri-propellant rocket engine comprises three main assemblies: an injector, a chamber head, and a chamber.

What is claimed is: 
     
         1 . A tri-propellant rocket engine for space launch applications comprising:
 an injector;   whereis said injector is an independent dual sleeve pintle injector that allows the independent control of velocity vector, momentum vector, liquid propellant pressure, propellant volument and vorticity;   a chamber head, wherein said chamber head serves as a mechanical support for said pintle injector and propellant injection manifolds;   and a chamber.   
     
     
         2 . The tri-propellant rocket engine according to  claim 1 , wherein adequate sizing of a sleeve area and a manifold area of said pintle injector allows said pintle injector to flexibly operate with any combination of propellants with minor calibration changes. 
     
     
         3 . The tri-propellant rocket engine according to  claim 1 , wherein changes can be made in flight provided an independent cooling path is maintained to prevent lox rich shutdown or thermal damage to the engine components. 
     
     
         4 . The tri-propellant rocket engine according to  claim 1 , wherein these two ideas are the core of a tri-propellant rocket engine which would switch between hydrocarbon fuel and hydrogen or between cryo propellant and hypergolic propellants. 
     
     
         5 . The tri-propellant rocket engine according to  claim 1 , wherein propellant source includes two fuel sources and an oxidizer source. 
     
     
         6 . The tri-propellant rocket engine according to  claim 5 , wherein said two fuel sources is selected from the group consisting of a liquid fuel, a gaseous fuel, a fluid fuel, a thixotropic or pseudoplastic material, and any combination thereof, and wherein said oxidizer source is selected from the group consisting of a liquid oxidizer, a powdered fluid oxidizer, a gaseous oxidizer, and any combination thereof. 
     
     
         7 . The tri-propellant rocket engine according to  claim 6 , wherein said liquid fuel is selected from the group consisting of monomethyl hydrazine (MMH), kerosene, methane, propane, ammonia, hydrogen and pentaborane.